CN207826569U - A kind of fixed-wing formula hybrid power aircraft driving device - Google Patents

Abstract

The utility model discloses a kind of fixed-wing formula hybrid power aircraft driving devices, are related to aviation aircraft technical field, including engine, planet row coupling device, arrangement of clutch, electric system, two-speed automatic transmission, propeller；Wherein arrangement of clutch includes No.1 clutch, No. two clutches and brake；Electric system includes No.1 motor, No. two motors, inverter and battery.The utility model has the characteristics that the preferably technology inheritance and fuel economy, low emission, low noise with existing fixed-wing formula aircraft, be operated alone with engine, Dual-motors Driving, variable speed and joint driving etc. multiple-working modes, solve the problems, such as that traditional fixed-wing formula airplane mode is single, special air mission noise reduction, noise reduction function may be implemented, it is easy to accomplish scale industrialization.

Description

A kind of fixed-wing formula hybrid power aircraft driving device

Technical field

The utility model is related to aviation aircraft technical field, more particularly to a kind of fixed-wing formula hybrid power aircraft drives Dynamic device.

Background technology

1 kilogram of fuel oil is often consumed when fixed-wing formula aircraft flight will discharge 3 kilograms of carbon dioxide, and gas directly exists Atmosphere discharges, and the influence to global warming discharges bigger than ground.Thus the motorized of aircraft and mixed dynamicization are imperative.Fly One important development direction of machine mobile system is electric power, that is, uses more electric systems and all electric system.At the same time, it promotes The electric powerization of system and power plant also makes substantial progress, and has been used successfully to small propeller general-purpose aircraft, fixed-wing Formula aircraft and unmanned plane.Electric airplane have energy conservation and environmental protection, high efficiency, it is simple in structure many advantages, such as, will push it is general fly Machine, unmanned plane realize revolutionary development.It is difficult merely to meet its power by electric energy however in fixed-wing formula aircraft field Property demand；Therefore applying for hybrid power is come into being in aircraft field.

Following aircraft will not only meet the needs of dynamic property, should also there is lower discharge and energy consumption.In fixed-wing The application in formula aircraft field, Technology of Hybrid Electric Vehicle efficiently solves the higher fuel consumption rate of traditional combustion engine and emission performance The shortcomings of poor, is gradually approved by industry.Its drive system of hybrid power aircraft has three kinds of forms of series, parallel and series-parallel connection. Series connection type hybrid power system has many advantages, such as that Powertrain control is simple, but because there are energy secondary conversions to lead in drive system The disadvantage for causing overall efficiency relatively low.Parallel connection type hybrid power system has the advantages that capacity usage ratio is higher, but in speed operation In, the working efficiency of engine is restricted.Series-parallel hybrid electric system summarizes the dual of two kinds of configurations of series connection and parallel connection Advantage has best comprehensive performance.Especially series-parallel hybrid electric system realizes electronic infinite variable speed function, and engine is realized The bilingual coupling of rotational speed and torque improves the overall performance of system to greatest extent.

Currently, the patent of existing fixed-wing formula hybrid power aeroplane is mostly simple in structure, function and pattern are single.As in State Patent publication No CN106314809A, date of publication 2017-01-11 disclose a kind of fixed-wing formula hybrid power aeroplane, this is System uses serial configured, simple in structure；But the system is single using pattern, energy demand two times transfer, and system overall efficiency is low. And its propeller can only rely on motor to drive, poor reliability, and motor demand power is high.Such as Chinese patent publication No. CN106184779A, date of publication 2016-12-07, disclose a kind of hybrid power aeroplane coupled system, which uses engine Combine driving with motor, capacity usage ratio is higher；But system working efficiency of engine in speed operation is restricted, and is driven Dynamic power demand of motors is big, oversized, and aircraft weight is caused to increase.The utility model proposes a kind of mixing of fixed-wing formula it is dynamic Power aircraft driving device combines Dual-motors Driving, electronic infinite variable speed, engine and combines driving and engine list with motor The solely multiple-working modes such as driving increase a variety of on the one hand while ensureing that conventional engines driving may be implemented in aircraft Operating mode further improves economy, dynamic property and the emission performance of system；On the other hand it is effectively reduced the flight of fixed-wing formula Device work noise realizes special air mission noise reduction, noise reduction function；In addition to this it is possible to realize Dual-motors Driving, bi-motor Brake energy recovery and engine driving and the isotype that generates electricity further improve the fuel economy of system.

Invention content

The utility model is that traditional fixed-wing formula airplane mode is single, course continuation mileage is short, economic performance and row to overcome The problems such as performance is poor is put, and is effectively reduced fixed-wing formula aircraft flight noise, it is dynamic to provide a kind of fixed-wing formula mixing Power aircraft driving device.

In order to solve the above technical problems, the utility model adopts the following technical scheme that realization, in conjunction with attached drawing：Described A kind of fixed-wing formula hybrid power aircraft driving device, including engine 1, power input shaft 3, power output shaft 21 and spiral Paddle 24, which is characterized in that a kind of fixed-wing formula hybrid power aircraft driving device further includes planet row coupling device I, two-speed automatic transmission II, arrangement of clutch and electric system；Wherein, the two-speed automatic transmission II includes level-one active Gear 13, level-one driven gear 14, two level driving gear 15, two level driven gear 16, lay shaft 17, clutch collar 18, flower Key hub 19 and case of transmission 20；Arrangement of clutch includes 9, No. two clutches 10 of No.1 clutch and brake 12；Electric system Including 4, No. two motors 11 of No.1 motor, inverter 22 and battery 23；Planet row coupling device I passes through 5 sets of planet row sun gear It is rotation connection on power input shaft 3；Two-speed automatic transmission II is by bearing holder (housing, cover) on power output shaft 21；Level-one Driving gear 13 is connect and is rotated jointly by spline or other forms with the rotor of No. two motors 11, and level-one driving gear 13 is left End is engagement gear ring structure；For two level driven gear 16 by bearing support in the optical axis portion of power output shaft 21, two level is driven 16 right end of gear is engagement gear ring structure；Lay shaft 17 is integrated knot with level-one driven gear 14 and two level driving gear 15 Structure；The shell of No.1 motor 4 is fixed on aircraft fuselage 25, and the rotor of No.1 motor 4 is sleeved on the right side of power input shaft 3 End, is connect and is rotated jointly by spline or other forms with planet row sun gear 5；The shell of No. two motors 11 is fixed on flight On device fuselage 25, the rotor of No. two motors 11 is sleeved on the right end of power output shaft 21.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein planet row coupling Attach together set I, power input shaft 3, No.1 motor 4, the clutch 10, two of No.1 clutch 9, two motor 11, brake 12 with The rotation conllinear of power output shaft 21.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein planet row coupling It includes planet row sun gear 5, planet row planetary gear 6, planet row planet carrier 7, planet row gear ring 8 to attach together and set I；The planet row Sun gear 5, planet row planetary gear 6, planet row gear ring 8 engage successively, and planet row planet carrier 7 is rotation with planet row planetary gear 6 Connection；8 right end axis extending portion of planet row gear ring point is connect by spline or other forms with 21 left end of power output shaft and is revolved jointly Turn.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein level-one is actively Gear 13 is hollow cylinder gear structure with two level driven gear 16, and level-one driving gear 13 is often nibbled with level-one driven gear 14 It closes, two level driving gear 15 is often engaged with two level driven gear 16, and lay shaft 17 is by bearing support in case of transmission In 20 through-hole；Clutch collar 18 is hollow ring structure, and hollow position is provided with internal tooth arrangement, is used for and engages gear ring and splined hub 19 Engagement；Splined hub 19 is hollow ring structure, and hollow position is provided with internal spline, connect and is total to power output shaft 21 by spline pair With rotation, outer circle is provided with outer toothing, for being engaged with clutch collar 18；Case of transmission 20 is fixed on aircraft fuselage 25.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein level-one is actively The rotation conllinear of gear 13, two level driven gear 16, clutch collar 18, splined hub 19 and power output shaft 21.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein two gears are automatic Speed changer II realizes two gear speed changes, respectively bottom gear and direct gear；Wherein, bottom gear passes through two-stage gear pair decelerating effect； For direct gear without decelerating effect, gear speed ratio is 1；When clutch collar 18 is centrally located, neutral gear is realized.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein No.1 clutch The active part of device 9 is fixedly connected with power input shaft 3, and the secondary part of No.1 clutch 9 is connected in planet row planet carrier 7 Right end is rotated jointly with planet row planet carrier 7；The active part of No. two clutches 10 passes through spline with 21 left end of power output shaft Or other forms are connected and are rotated jointly, the active part of the secondary part and No.1 clutch 9 of No. two clutches 10 is integrated Structure；The active part of brake 12 is connect and is rotated jointly by spline or other forms with power input shaft 3, secondary part It is fixed on aircraft fuselage 25.

According to a kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, wherein No.1 motor 4 Make turning for engine 1 for decoupling the rotating speed between engine 1 and propeller 24 under different operating modes for permanent magnet synchronous motor Speed is independently of the rotating speed of propeller 24, torque decoupler of No. two motors 11 of cooperation between engine 1 and propeller 24, guarantee hair Motivation 1 works in efficient region, to improve fuel economy；No. two motors 11 are permanent magnet synchronous motor, and No. two motors 11 have High torque (HT) output characteristics decouples the torque output of engine 1 from duty requirements torque and comes out, and releases engine 1 and power Because of limitation of the duty requirements torque to 1 torque of engine caused by mechanical connection between output shaft 21；Inverter 22 according to The selection of the voltage class of No.1 motor 4 and No. two motors 11；Three connectors of No.1 motor 4 pass through cable and inverter respectively 22 three alternating current input/output connectors connection, the positive and negative connector of inverter 22 are positive and negative using cable and battery 23 Pole connects, and three connectors of No. two motors 11 pass through the other three alternating current input/output of cable and inverter 22 respectively Connector connects.

A kind of fixed-wing formula hybrid power aircraft driving device provided by the utility model, including engine individually drive Dynamic, Dual-motors Driving, electronic infinite variable speed, engine driving and generate electricity, engine combine driving with motor and bi-motor is braked Six kinds of main operation modes such as energy regenerating.

The utility model compared with prior art, has the beneficial effect that：

1. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is by engaging No.1 clutch Device and brake, and two-speed automatic transmission is linked into gear, it realizes Dual-motors Driving, under specific run operating mode, realizes and fly Row device low noise improves system fuel economy, while reducing harmful gas emission, reduces the pollution to environment.

2. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is by engaging No.1 clutch Device, and two-speed automatic transmission is linked into gear, electronic infinite variable speed may be implemented, overall efficiency is high in low regime, and protects Card engine is operated in best fuel-economy area, improves course continuation mileage.

3. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is by engaging No. two clutches Device, and two-speed automatic transmission is linked into gear, may be implemented that engine combines driving with motor, engine is operated alone and sends out Motivation driving and power generation mode realize that engine joins with motor according to fixed-wing formula craft power demand and battery charge state The switching with engine driving and power generation mode is operated alone in conjunction driving, engine.

4. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is braked by engaging No.1 Device, and two-speed automatic transmission is linked into gear, bi-motor Brake energy recovery may be implemented, hence it is evident that improve system fuel-economy Property, improve course continuation mileage.

5. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model can select smaller power Engine meet the normal flight requirement of fixed-wing formula aircraft, reduce harmful gas emission, reduce the dirt to environment Dye.

6. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model can under specific operation, It realizes that Dual-motors Driving and engine are operated alone, improves the fault tolerance of power source and related system, improve fixed-wing formula Aircraft flight safety and mobility.

7. a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model has a wide range of application, it is suitable for The fixed-wings formula aircraft such as fixed-wing formula aircraft, including aircarrier aircraft, military aircraft, unmanned plane field.

Description of the drawings

The utility model is described in further detail below in conjunction with the accompanying drawings：

Fig. 1 is a kind of structure principle chart of fixed-wing formula hybrid power aircraft driving device described in the utility model；

Fig. 2 is that a kind of fixed-wing formula hybrid power aircraft driving device engine described in the utility model is operated alone Under structure principle chart；

Fig. 3 is that a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is low in Dual-motors Driving Structure principle chart under speed gear；

Fig. 4 is that a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is straight in Dual-motors Driving Connect the structure principle chart under gear；

Fig. 5 is a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model in electronic infinite variable speed Structure principle chart under bottom gear；

Fig. 6 is a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model in electronic infinite variable speed Structure principle chart under direct gear；

Fig. 7 be a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model engine driving simultaneously Structure principle chart under power generation mode bottom gear；

Fig. 8 be a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model engine driving simultaneously Structure principle chart under power generation mode direct gear；

Fig. 9 is a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model in engine and motor Structure principle chart under joint driving bottom gear；

Figure 10 is a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model in engine and electricity Structure principle chart under machine joint driving direct gear；

Figure 11 is that a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is braked in bi-motor Structure principle chart under energy regenerating bottom gear；

Figure 12 is that a kind of fixed-wing formula hybrid power aircraft driving device described in the utility model is braked in bi-motor Structure principle chart under energy regenerating direct gear；

In figure：1. engine, 2. torsional vibration dampers, 3. power input shafts, 4. No.1 motors, 5. planet row sun gears, 6. Planet row planetary gear, 7. planet row planet carriers, 8. planet row gear rings, 9. No.1 clutches, 10. No. two clutches, 11. No. two electricity Machine, 12. brakes, 13. level-one driving gears, 14. level-one driven gears, 15. two level driving gears, 16. two level driven gears, 17. lay shaft, 18. clutch collars, 19. splined hubs, 20. case of transmission, 21. power output shafts, 22. inverters, 23. electricity Pond, 24. propellers, 25. aircraft fuselages, I, planet row coupling devices, II, two-speed automatic transmissions.

Specific implementation mode

The utility model is explained in detail below in conjunction with the accompanying drawings：

Refering to fig. 1, Fig. 2, the utility model provides a kind of fixed-wing formula hybrid power aircraft driving device, described A kind of fixed-wing formula hybrid power aircraft driving device includes mainly engine, planet row coupling device, arrangement of clutch, motor System, two-speed automatic transmission, power input shaft, power output shaft and propeller, wherein planet row coupling device include planet Arrange sun gear, planet row planetary gear, planet row planet carrier and planet row gear ring；Arrangement of clutch include No.1 clutch, No. two from Clutch, brake；Electric system includes No.1 motor, No. two motors, inverter, batteries；Two-speed automatic transmission includes speed change Device shell, level-one driving gear, level-one driven gear, two level driving gear, two level driven gear, lay shaft, clutch collar And splined hub.

Refering to fig. 1, the planet row coupling device I includes power input shaft 3, planet row sun gear 5, planet seniority among brothers and sisters Star-wheel 6, planet row planet carrier 7, planet row gear ring 8.

Refering to fig. 1, the power input shaft 3 be multidiameter structure, left end be provided with external splines for transmit come from start Machine 1 passes through the power of torsional vibration damper 2, and right end imparts power to No.1 clutch 9 and No. two by spline or other forms Clutch 10；The planet row sun gear 5 is roller gear structure；The planet row planetary gear 6 is roller gear structure； The planet row planet carrier 7 is circular ring structure, is structure as a whole with the secondary part of No.1 clutch 9；The planet row Gear ring 8 is cylinder inner gear ' structure, and right end axis extending portion point is connect with power output shaft 21 by spline or other forms and common Rotation.

Refering to fig. 1, for 3 left end of power input shaft by bearing support in the output end of torsional vibration damper 2, right end passes through bearing It is supported in 9 groove of No.1 clutch；Planet row sun gear 5 by bearing support power input shaft 3 optical axis portion, with row Star is ranked star-wheel 6 and is often engaged；Planet row planetary gear 6 is often engaged with planet row sun gear 5 and planet row gear ring 8 respectively；Planet row Planet carrier 7 is connect by axis pin with planet row planetary gear 6, and is revolved round the sun around planet row sun gear 5.

Refering to fig. 1, the arrangement of clutch includes 9, No. two clutches 10, brakes 12 of No.1 clutch.

Refering to fig. 1, the No.1 clutch 9 and No. two clutches 10 are integrated in planet row coupling device I；Described No.1 clutch 9 is multi-plate friction clutch, and active part is fixedly connected with power input shaft 3, secondary part and planet Seniority among brothers and sisters carrier 7 is fixed together, and No.1 clutch 9 is engaged by rubbing action；No. two clutches 10 be multiple-piece friction from Clutch, active part are connect and are rotated jointly by spline or other forms with power output shaft 21, secondary part and No.1 The active part of clutch 9 is structure as a whole, and No. two clutches 10 are engaged by rubbing action；The brake 12 is more Flake friction braker, active part are connect and are rotated jointly by spline or other forms with power input shaft 3, follower Divide and be fixed on aircraft fuselage 25, by rubbing action come engagement brake 12.

Refering to fig. 1, Fig. 3, the electric system include 4, No. two motors 11, inverter 22, batteries 23 of No.1 motor.

Refering to fig. 1, Fig. 3, the No.1 motor 4 are permanent magnet synchronous motor, and the shell of No.1 motor 4 is fixed on aircraft On fuselage 25, motor output shaft is hollow shaft, by bearing support in the optical axis portion of power input shaft 3, rotor and row Star row's sun gear 5 is connected and is rotated jointly by spline or other forms；The No.1 motor 4 under different operating modes for solving Rotating speed between coupling engine 1 and propeller 24 makes the rotating speed of engine 1 independently of the rotating speed of propeller 24, coordinates No. two electricity Torque decoupler of the machine 11 between engine 1 and propeller 24, it is ensured that engine 1 works in efficient region, to improve combustion Oily economy.No. two motors 11 are permanent magnet synchronous motor, and the shell of No. two motors 11 is fixed on aircraft fuselage 25, For motor output shaft by bearing support in the through-hole of case of transmission 20, rotor passes through spline with level-one driving gear 13 Or other forms are connected and are rotated jointly；No. two motors 11 can increase with high torque (HT) output characteristics to be come from propeller 24 The torque output of engine 1 is solved decoupling by the torque of engine 1 to meet operating mode torque-demand from duty requirements torque Come, relieves between engine 1 and power output shaft 21 because duty requirements torque caused by mechanical connection is to 1 turn of engine The limitation of square.

Refering to fig. 1, Fig. 3, the inverter 22 are selected according to the voltage class of No.1 motor 4 and No. two motors 11.Institute Three connectors of the No.1 motor 4 stated pass through three alternating current input/output connector x, y, z of cable and inverter 22 respectively Connection, the positive and negative connector of inverter 22 are connect using cable with the positive and negative anodes of battery 23, three connectors of No. two motors 11 It is connect respectively with the other three alternating current input/output connector x ', y ', the z ' of inverter 22 by cable.

Refering to fig. 1, the two-speed automatic transmission II includes level-one driving gear 13, level-one driven gear 14, two Grade driving gear 15, two level driven gear 16, lay shaft 17, clutch collar 18, splined hub 19 and case of transmission 20；It is described Two-speed automatic transmission II two gear speed changes, respectively bottom gear and direct gear may be implemented；Wherein, bottom gear subtracts by two-stage Fast torque effect, direct gear speed ratio are 1.

Refering to fig. 1, the level-one driving gear 13 and two level driven gear 16 are hollow cylinder gear structure, level-one 13 left end of driving gear is engagement gear ring structure, and 16 right end of two level driven gear is engagement gear ring structure；Level-one driven gear 14 It is roller gear structure with two level driving gear 15；Lay shaft 17 be multidiameter structure, with level-one driven gear 14 with Two level driving gear 15 is structure as a whole；Clutch collar 18 is hollow ring structure, and hollow position is provided with internal tooth arrangement, is used for and engagement Gear ring and splined hub 19 engage；Splined hub 19 is hollow ring structure, and hollow position is provided with internal spline, defeated with power by spline pair Shaft 21 is connected and is rotated jointly, and outer circle is provided with outer toothing, for being engaged with clutch collar 18；Case of transmission 20 is hull shape knot Structure, prolongs power output shaft 21 and 17 central axial direction of lay shaft is provided with through-hole.

Refering to fig. 1, the level-one driving gear 13 is connect with the rotor of No. two motors 11 by spline or other forms And rotate jointly, two level driven gear 16 by bearing support power output shaft 21 optical axis portion；Level-one driving gear 13 It is often engaged with level-one driven gear 14, two level driving gear 15 is often engaged with two level driven gear 16；Lay shaft 17 passes through Bearing support is in the through-hole of case of transmission 20；Case of transmission 20 is fixed on aircraft fuselage 25.

Refering to fig. 1, clutch collar 18 is controlled by controller to horizontally slip；When clutch collar 18 slide into left side gear, i.e., it is low When speed gear, 16 right end of two level driven gear engagement gear ring is fixedly connected and rotates jointly with splined hub 19, No. two motors 11 it is defeated Go out torque respectively after the double reductions torques such as one-stage gear pair, secondary gear wheel set, is output to power output shaft 21；Work as engagement When set 18 slides into right side gear, i.e. direct gear, 13 left end of level-one driving gear engagement gear ring is fixedly connected simultaneously with splined hub 19 It rotates jointly, the output torque of No. two motors 11 is directly output to power output shaft 21, at this time one-stage gear pair, secondary gear wheel set In idling conditions；When clutch collar 18 slides into intermediate gear, i.e. neutral gear, cut off between No. two motors 11 and power output shaft 21 Power transmit.

Operation principle is divided with operating mode

Refering to fig. 1, a kind of fixed-wing formula hybrid power aircraft driving device has 3 power inputs, is respectively Engine 1, No.1 motor 4 and No. two motors 11；The power of engine is inputted by power input shaft 3, the power of No.1 motor 4 It is inputted by planet row sun gear 5, the power of No. two motors 11 is inputted by level-one driving gear 13.

A kind of operating mode of fixed-wing formula hybrid power aircraft driving device described in the utility model comes with energy Source is as shown in table 1：

1. operating mode of table and energy source

The clutch of fixed-wing formula hybrid power aircraft driving device described in the utility model a kind of, brake connect Conjunction state is as shown in table 2：

2. Clutch and brake state of table

Wherein, zero engagement is represented, × represent separation.

Concrete operating principle is divided into main operation modes：

1, engine is operated alone

Refering to fig. 1, Fig. 2, the engine are operated alone under pattern, hybrid power aircraft and traditional combustion engine aircraft work Operation mode is identical.Engine, which is operated alone, is mainly used for the flights operating modes such as battery capacity deficiency, electric system failure；At engine 1 In working condition, clutch controller controls No. two clutches 10 and engages, and No.1 motor 4 and No. two motors 11 do not work；It is sending out Motivation is operated alone down, and engine 1 exports power and inputted by power input shaft 3, and by No. two clutches 10, it is defeated to be output to power Shaft 20 and then driving propeller；No.1 clutch 9 and brake 12 are in discrete state at this time；Engine is operated alone can be with So that system obtains higher system overall efficiency, and prevent energy from two times transfer occurs.When fixed-wing formula flying vehicle electric systemic Break down or battery capacity be less than minimum amount of power threshold value when, engine, which is operated alone, can ensure aircraft according to traditional mould Formula is flown and safe landing.

2, Dual-motors Driving

Refering to fig. 1, Fig. 3, Fig. 4, Dual-motors Driving are mainly used for low noise flight, engine system failure and fuel shortage Equal flights operating mode.Under Dual-motors Driving pattern, engine 1 is in off-mode, and No.1 motor 4 is electronic, No. two 11 electricity of motor Dynamic, No.1 clutch 9 and brake 12 engage；Under Dual-motors Driving, 4 power of No.1 motor is inputted by planet row sun gear 5, Power output shaft 21 is output to after planet row coupled system I；No. two 11 power of motor are inputted by level-one driving gear 13, warp After crossing two-speed automatic transmission II, it is output to power output shaft 21；The two torque is superimposed driving spiral at power output shaft 21 Paddle 24；When aircraft engine system cisco unity malfunction, such as engine 1 breaks down or the case where fuel shortage Under, Dual-motors Driving can ensure flight and the safe landing in short-term under pure electric vehicle of fixed-wing formula aircraft.

Refering to Fig. 3, Fig. 4, Dual-motors Driving is divided into bottom gear and direct gear, and aircraft acquires spiral by master controller Paddle rotating speed and demand torque, then send commands to gearbox controller, and gearbox controller controls clutch collar 18 and kept off certainly to two Dynamic speed changer II carries out gear shifting action；Wherein, bottom gear is suitable for low rotation speed large torque operating mode, and it is small that direct gear is suitable for high rotating speed Torque operating mode.

Refering to fig. 1, Fig. 3, Fig. 4, for the higher aircraft of the flights demand power such as airliner, military aircraft, preferably Dual-motors Driving ensures output power of motor meet demand power；And for the small aircrafts such as unmanned plane, flight demand work( Rate is small, can select that No.1 motor is operated alone or No. two motors are operated alone as needed.For the ordinary skill of this field For personnel, corresponding change and different selections can be made as the case may be.

3, electronic infinite variable speed

Refering to fig. 1, Fig. 5, Fig. 6, electronic infinite variable speed are mainly used for the common flight operating modes such as constant speed flight, cruise；In electricity Under sub- stepless shift mode, engine 1 is in running order, and No.1 motor 4 is in generating state, and No. two motors 11 are in electronic State；No.1 clutch 9 engages, and No. two clutches 10 and brake 12 detach；Under electronic infinite variable speed, engine 1 it is defeated Go out power and be divided into two parts, a part passes through planet row gear ring 8, is output to power output shaft 21；Another part passes through planet row Sun gear 5 is output to No.1 motor 4.No.1 motor 4 is in generating state, and the mechanical energy that engine 1 transmits is converted to electricity Can, electric energy passes to No. two motors 11 and battery 23 by power path.No. two motors 11 are in motoring condition, by No.1 motor 4 The electric energy transmitted with battery 23 is converted to mechanical energy, is inputted by level-one driving gear 13, is kept off by two-speed automatic transmission II Behind position, final output to power output shaft 21；Engine 1 and the mechanical energy of No. two motors 11 output are folded at power output shaft 21 Add coupling, final output to propeller 24.

Refering to Fig. 5, Fig. 6, electronic infinite variable speed is divided into bottom gear and direct gear, and aircraft acquires spiral shell by master controller Paddle rotating speed and demand torque are revolved, gearbox controller is then sent commands to, gearbox controller controls clutch collar 18 and kept off to two Automatic transmission II carries out gear shifting action；Wherein, bottom gear is suitable for low rotation speed large torque operating mode, and direct gear is suitable for high rotating speed Small torque operating mode.

4, it engine driving and generates electricity

Refering to fig. 1, Fig. 7, Fig. 8, engine driving and power generation mode are mainly used for the flights work such as high-speed flight, battery supply feed Condition.Under engine driving and power generation mode, engine 1 is in running order, and clutch controller controls No. two clutches 10 Engagement, No.1 motor 4 do not work, and No. two motors 11 generate electricity, and charge to battery 23 by cable and inverter 22, No.1 clutch Device 9 and brake 12 detach；Under engine driving and power generation mode, engine 1 exports power and is inputted by power input shaft 3, A part passes through 21 direct output driving propeller 24 of power output shaft；Another part passes through II gear of two-speed automatic transmission Afterwards, it converts mechanical energy to electric energy by No. two motors 11, is stored into battery 23；When fixed-wing formula flying vehicle electric systemic occurs When failure or battery supply feed, simultaneously power generation mode can ensure that aircraft flies and fills according to traditional mode to engine driving Electricity, the pattern are suitable for the smaller flight operating mode of flight demand power.

Refering to Fig. 7, Fig. 8, simultaneously power generation mode is divided into bottom gear and direct gear to engine driving, and aircraft is controlled by center Device acquires revolution speed of propeller and demand torque, then sends commands to gearbox controller, and gearbox controller controls clutch collar 18 pairs of two-speed automatic transmissions II carry out gear shifting action, and motor operating point is made to be in high efficient area.

5, engine combines driving with motor

Refering to fig. 1, Fig. 9, Figure 10, engine combine driving with motor and are mainly used for accelerating take off, climb, accelerating flight etc. High-power flight operating mode.In the case where engine combines drive mode with motor, engine 1 is in running order, clutch controller No. two clutches 10 of control engage, and No.1 motor 4 does not work, and No. two motors 11 are electronic, and No.1 clutch 9 and brake 12 divide From；In the case where engine combines driving with motor, engine 1 exports power and is inputted by power input shaft 3, by No. two clutches 10 It is transmitted to power output shaft 21；Battery 23 is that No. two motors 11 provide electric energy, and the two power couples at power output shaft 21；When When fixed-wing formula flying vehicle electric systemic battery capacity abundance, engine, which combines driving with motor, can meet fixed-wing formula aircraft It takes off, climb, accelerating the high-power flight operating modes such as flight, landing.

Refering to Fig. 9, Figure 10, engine combines driving with motor and is divided into bottom gear and direct gear, and aircraft is controlled by center Then device acquisition revolution speed of propeller processed and demand torque send commands to gearbox controller, gearbox controller control engagement 18 pairs of two-speed automatic transmissions II of set carry out gear shifting action；Wherein, bottom gear is suitable for low rotation speed large torque operating mode, and direct gear is suitable For the small torque operating mode of high rotating speed.

6, bi-motor Brake energy recovery

Refering to fig. 1, Figure 11, Figure 12, bi-motor Brake energy recovery are mainly used for the ground damped conditions such as sliding race.In double electricity Under mechanism energy pattern, engine 1 is in off-mode, and No.1 motor 4 and No. two motors 11 generate electricity, by cable and inverse Become device 22 to charge to battery 23, No.1 clutch 9 and brake 12 engage；Under bi-motor Brake energy recovery, power is by spiral shell It revolves paddle 24 to input, a part is output to No. two motors 11 for generating electricity, another part passes through after two-speed automatic transmission II Planet row coupling device I is output to No.1 motor 4 for generating electricity.

Under the ground damped conditions such as sliding race, controller counts the factors such as severity of braking, state-of-charge, rotary speed information It calculates, judge and arbitrates.Turn if fixed-wing formula aircraft brakes demand torque is more than the maximum braking that electric system can be provided When square, the part in brake force is provided by electric system, mechanical energy is converted to electric energy, and be stored in battery, system Another part in power is provided by deceleration devices such as spoiler and flaps.

Term " first ", " second " are used for description purposes only, be not understood to indicate or imply relative importance or Implicitly indicate the quantity of indicated technical characteristic.In the present invention unless specifically defined or limited otherwise, term The terms such as " installation ", " connected ", " connection ", " fixation " shall be understood in a broad sense, for example, it may be being fixedly connected, can also be can Dismantling connection, or can be integrally mechanical connection, it can also be to be electrically connected or can communicate each other can be directly connected, also may be used Indirectly connected through an intermediary, can be the interaction relationship of connection or two elements inside two elements, unless Separately there is specific restriction.For the ordinary skill in the art, above-mentioned term can be understood at this as the case may be Concrete meaning in utility model.

Various other combinations, modification are made to operating mode on the basis of the above description.Here no longer to all implementations Combination is exhaustive.And the protection domain that the obvious changes or variations thus amplified out are created still in the utility model Among.

Claims (8)

1. a kind of fixed-wing formula hybrid power aircraft driving device, including engine (1), power input shaft (3), power output Axis (21) and propeller (24), which is characterized in that a kind of fixed-wing formula hybrid power aircraft driving device further includes Planet row coupling device (I), two-speed automatic transmission (II), arrangement of clutch and electric system；Wherein, two gears are automatic becomes Fast device (II) includes level-one driving gear (13), level-one driven gear (14), two level driving gear (15), two level driven gear (16), lay shaft (17), clutch collar (18), splined hub (19) and case of transmission (20)；Arrangement of clutch include No.1 from Clutch (9), No. two clutches (10) and brake (12)；Electric system includes No.1 motor (4), No. two motors (11), inversions Device (22) and battery (23)；

The planet row coupling device (I) is sleeved on by planet row sun gear (5) on power input shaft (3) to be connected for rotation It connects；Two-speed automatic transmission (II) is by bearing holder (housing, cover) on power output shaft (21)；Level-one driving gear (13) and No. two electricity The rotor of machine (11) is connected and is rotated jointly by spline or other forms, and level-one driving gear (13) left end is soldered tooth loop knot Structure；Optical axis portion of the two level driven gear (16) by bearing support in power output shaft (21), two level driven gear (16) are right End is engagement gear ring structure；Lay shaft (17) is integrated knot with level-one driven gear (14) and two level driving gear (15) Structure；The shell of No.1 motor (4) is fixed on aircraft fuselage (25), and the rotor of No.1 motor (4) is sleeved on power input shaft (3) right end is connect and is rotated jointly by spline or other forms with planet row sun gear (5)；The shell of No. two motors (11) Body is fixed on aircraft fuselage (25), and the rotor of No. two motors (11) is sleeved on the right end of power output shaft (21).

2. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described Planet row coupling device (I), power input shaft (3), No.1 motor (4), No.1 clutch (9), No. two clutches (10), No. two The rotation conllinear of motor (11), brake (12) and power output shaft (21).

3. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described Planet row coupling device (I) includes planet row sun gear (5), planet row planetary gear (6), planet row planet carrier (7), planet toothrow It encloses (8)；The planet row sun gear (5), planet row planetary gear (6), planet row gear ring (8) engage successively, planet rows of planetary Frame (7) is rotation connection with planet row planetary gear (6)；Planet row gear ring (8) right end axis extending portion point is left with power output shaft (21) End is connected and is rotated jointly by spline or other forms.

4. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described Level-one driving gear (13) and two level driven gear (16) are hollow cylinder gear structure, level-one driving gear (13) and level-one from Moving gear (14) often engages, and two level driving gear (15) is often engaged with two level driven gear (16), and lay shaft (17) passes through Bearing support is in the through-hole of case of transmission (20)；Clutch collar (18) is hollow ring structure, and hollow position is provided with internal tooth arrangement, For being engaged with engagement gear ring and splined hub (19)；Splined hub (19) is hollow ring structure, and hollow position is provided with internal spline, passes through Spline pair connect and rotates jointly with power output shaft (21), and outer circle is provided with outer toothing, for being engaged with clutch collar (18)；Become Fast device shell (20) is fixed on aircraft fuselage (25).

5. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 4, which is characterized in that described The revolution of level-one driving gear (13), two level driven gear (16), clutch collar (18), splined hub (19) and power output shaft (21) Axis collinear.

6. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described Two-speed automatic transmission (II) realizes two gear speed changes, respectively bottom gear and direct gear；Wherein, bottom gear passes through two-stage gear pair Decelerating effect；For direct gear without decelerating effect, gear speed ratio is 1；When clutch collar (18) is centrally located, neutral gear is realized.

7. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described The active part of No.1 clutch (9) is fixedly connected with power input shaft (3), and the secondary part of No.1 clutch (9) is connected in The right end of planet row planet carrier (7) is rotated jointly with planet row planet carrier (7)；The active part of No. two clutches (10) with it is dynamic Power output shaft (21) left end is connected and is rotated jointly by spline or other forms, the secondary part and one of No. two clutches (10) The active part of number clutch (9) is structure as a whole；The active part of brake (12) and power input shaft (3) by spline or Other forms are connected and are rotated jointly, and secondary part is fixed on aircraft fuselage (25).

8. a kind of fixed-wing formula hybrid power aircraft driving device according to claim 1, which is characterized in that described No.1 motor (4) is permanent magnet synchronous motor, is turned between engine (1) and propeller (24) for being decoupled under different operating modes Speed makes the rotating speed of engine (1) independently of the rotating speed of propeller (24), and No. two motors (11) of cooperation are to engine (1) and spiral Torque decoupler between paddle (24) ensures that engine (1) works in efficient region, to improve fuel economy；No. two motors (11) it is permanent magnet synchronous motor, No. two motors (11) have high torque (HT) output characteristics, the torque output of engine (1) from operating mode Decoupling comes out in demand torque, releases between engine (1) and power output shaft (21) because of operating mode caused by mechanical connection Limitation of the demand torque to engine (1) torque；Inverter (22) according to No.1 motor (4) and No. two motors (11) voltage etc. Grade selection；Three connectors of No.1 motor (4) are connect by three alternating current input/output of cable and inverter (22) respectively Head connection, the positive and negative connector of inverter (22) connect using cable with the positive and negative anodes of battery (23), No. two motors (11) Three connectors are connect by cable with the other three alternating current input/output connector of inverter (22) respectively.